振荡翼型/襟翼绕流数值研究  

作　　者：张馨元 

机构地区：[1]中国商飞上海飞机设计研究院,上海201210

出　　处：《科技创新导报》2017年第29期14-19,共6页Science and Technology Innovation Herald

摘　　要：采用Roe通量微分分裂格式离散Navier-Stokes(N-S)方程组的对流项,用统一时间步长的伪时间子迭代隐式LU-SGS方法进行时间推进,利用变形网格方法求解任意拉格朗日-欧拉(ALE)坐标下的N-S方程组,对NACA-0012翼型小幅振荡和动态失速以及三段翼型振荡襟翼等非定常流动进行了数值分析;通过与可获得的实验结果对比,吻合良好。与此同时,还对比分析了代数B-L、两方程SST及k-g等三种湍流模式的表现,总体上SST和k-g模式结果优于B-L模式;在动态失速流动中,SST模式较k-g模式更靠近测量值;采用SST模式对三段翼型振荡襟翼流场进行详细研究,分析流动特点及其与升力特性之间的关系。The Roe’s Flux Difference Splitting is employed as the spatial discretization scheme for the convective terms of the Navier-Stokes equations.The fully implicit lower-upper symmetric-Gauss-Seidel with pseudo time sub-iteration is applied as the temporal marching methods for both N-S equations and turbulence model equations.Flows around pitching airfoils or flap are investigated by solving N-S equations based on a moving grid system which described by Arbitrary Largangian-Eulerian method.Three turbulence models,such as algebraic Baldwin-Lomax,two-equation shear stress transport(SST)and k-g models,are employed to study the flows around pitching and dynamic stall NACA-0012,and the pitching flap of the three-element airfoil.The SST and k-g models perform better than B-L model.In the dynamic stall case,the SST model is better than the k-g model.Flowfields and flow characteristics of the pitching flap are investigated in detail by SST with respect to lift coefficients.

关 键 词：动网格 深失速 振荡翼型/襟翼 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]